setting reference values to find Cd, Cl, Cm (3D)
I'm trying to simulate a small experimental rocket (1,5m tall) in order t oget its aerodynamic coeff (Cd, Cl, and Cm at low angle of attack : 1°).
The problem is that I have a Cd=2500 !!
I think that may come from the ref. values...
Here is my mesh : http://img145.imageshack.us/img145/9...illage15dv.png
What sould I fill in area ? The cross area, or total area ? And for lenght... ?
I've computed from my environment (a half cylinder, in pressure far filed).
Any help is welcome !!
Thank you !!
|All times are GMT -4. The time now is 09:01.|